Snecma

Safran Aircraft Engines

Snecma Moteurs

Snecma Services

Didier Noel Durand

Dominique Gehan

Guy Lapergue

Valerie Annie Gros

Eric Herzer

Olivier Jean Daniel Baumas

Thierry Michel Breugnot

Thibault Jamon

Florence Irene Noelle Leutard

Raphael Curtelin

Marc Doussinault

Patrick Jacques Rossi

Didier Sotto-Lamy

Valérie Anne Gros

A turbomachine casing () comprising an endoscopy port () and a member () mounted on and fixed to the casing and comprising a duct () that communicates with the port and that comprises an internal thread into which a cap () can be screwed, and means () for fixing the member to the casing, characterised in that it further comprises a cover () mounted on the member and at least partially covering the fixing means in order to hinder, or indeed prevent, access to same when the cover is mounted on the member, the cover being arranged to allow free access to the duct when the cap is not screwed into the duct.

Turbomachine casing comprising an endoscopy port

A device for preventing rotation of a segment of nozzle guide vanes assembly in a form of an annulus sector housed inside an annular casing of a turbo machine with interposing of a heat shield sheet between an internal wall of the casing and an external wall of the segment of nozzle guide vanes assembly, the device including a rotation-proofing peg fitted both into a notch formed in the segment of nozzle guide vanes assembly and in a housing formed in the casing, the heat shield sheet including a tab resting against the rotation-proofing peg. A surface portion radially between the tab and the internal wall of the casing forms an end stop in event of a possible radial movement of the heat shield sheet while the turbo machine is in operation.

Turbo machine with a device for preventing a segment of nozzle guide vanes assembly from rotating in a casing; rotation-proofing peg

A blade sector of a turbine distributor to be carried by a turbine casing of an aeronautical turbine engine, including a front connection mechanism and a rear connection mechanism, wherein the front connection mechanism is adapted so as to bear against a holder carried by the turbine casing. The sector further includes an anti-wear device formed by a piece of a metal material surrounding the front end of the front connection mechanism and provided between the front connection mechanism and the holder to ensure a sliding contact between the two parts. The anti-wear device is axially maintained in position on the blade sector using an attachment mechanism engaging with the front connection mechanism.

Anti-wear device for the blades of a turbine distributor in an aeronautical turbine engine

Device for attaching ring sectors () to a turbine casing () in a turbomachine, comprising, at the upstream ends of the ring sectors (), circumferential coupling means () engaged on a casing rail () and clamped axially onto the casing rail by a C-section annular locking member () engaged axially on the casing rail and on the ring sector coupling means.

Device for attaching ring sectors to a turbine casing of a turbomachine

A device for attaching ring sectors around a turbine rotor in a turbomachine is disclosed. Each of the ring sectors includes at its upstream end a circumferential rim being able to be held on an annular casing rail by an annular locking member, and at its downstream end a pressing part that can press axially against a fixed element of the turbine to prevent the upstream rim of the ring sector from disengaging from the locking member in the event of considerable wear of the rail.

Device for attaching ring sectors around a turbine rotor of a turbomachine

The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstream of said afterburn chamber, each circle of flaps comprising alternately a plurality of controlled flaps, and a plurality of follower flaps, a circle of cold flaps arranged radially outside said nozzle and hinged at their upstream end to a conical shell linked to the downstream part of the casing. The means of cooling the divergent flaps comprise an annular plenum chamber delimited downstream by said conical shell and fed with cooling air through drillings made in a boundary wall between said plenum chamber and the downstream end of said annular passage, a plurality of distribution cells surrounding the plenum chamber and linked to the latter, said cells being delimited downstream by said conical shell and being arranged around the X axis in the planes of symmetry of the follower flaps and telescopic pipelines each linking a cell to the follower divergent flap situated in the same plane of symmetry as said cell.

Ventilation system for a convergent divergent exhaust nozzle

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Pontault Combault, France

Didier Noel Durand